New quick computation method of low speed and high AOA aerodynamic and research on engineering application

Zong Bin Zhang; Zheng Hong Gao; Qing Shi

New quick computation method of low speed and high AOA aerodynamic and research on engineering application

Zong Bin Zhang, Zheng Hong Gao, Qing Shi

School of Aeronautics

Research output: Contribution to journal › Article › peer-review

Abstract

Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncompressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.

Original language	English
Pages (from-to)	541-545
Number of pages	5
Journal	Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica
Volume	25
Issue number	4
State	Published - Dec 2007

Keywords

AOA
Nonlinear
Potential flow
Separated flow

Cite this

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title = "New quick computation method of low speed and high AOA aerodynamic and research on engineering application",

abstract = "Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncompressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.",

keywords = "AOA, Nonlinear, Potential flow, Separated flow",

author = "Zhang, {Zong Bin} and Gao, {Zheng Hong} and Qing Shi",

year = "2007",

month = dec,

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volume = "25",

pages = "541--545",

journal = "Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica",

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AU - Zhang, Zong Bin

AU - Gao, Zheng Hong

AU - Shi, Qing

PY - 2007/12

Y1 - 2007/12

N2 - Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncompressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.

AB - Based on the potential theory, a linearity combination of the disturbance flow field generated by the uncompressible vortex part was applied in the computation of separate vortex flow. As the computation of single wing-surface, combined wing-surfaces and FC-1 aircraft showed, this low speed and high AOA aerodynamic computing method given in this paper is effective in the range of stall AOA.

KW - AOA

KW - Nonlinear

KW - Potential flow

KW - Separated flow

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SN - 0258-1825

VL - 25

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JO - Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica

JF - Kongqi Donglixue Xuebao/Acta Aerodynamica Sinica

IS - 4

ER -

New quick computation method of low speed and high AOA aerodynamic and research on engineering application

Abstract

Keywords

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